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WO2001048439A2 - Procede et systeme de radiometrie interferometrique bi-dimensionnelle - Google Patents

Procede et systeme de radiometrie interferometrique bi-dimensionnelle Download PDF

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Publication number
WO2001048439A2
WO2001048439A2 PCT/US2000/033294 US0033294W WO0148439A2 WO 2001048439 A2 WO2001048439 A2 WO 2001048439A2 US 0033294 W US0033294 W US 0033294W WO 0148439 A2 WO0148439 A2 WO 0148439A2
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Prior art keywords
signal
roi
interferometric fringe
thermal emission
recited
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WO2001048439A3 (fr
Inventor
Carter M. Glass
Arthur Casimir Golubiewski
Lori K. Harrison
Scott David Alexander
Christopher Taylor Herring
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Lockheed Martin Corp
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Lockheed Corp
Lockheed Martin Corp
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Priority to AU55149/01A priority Critical patent/AU5514901A/en
Publication of WO2001048439A2 publication Critical patent/WO2001048439A2/fr
Publication of WO2001048439A3 publication Critical patent/WO2001048439A3/fr
Anticipated expiration legal-status Critical
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    • G—PHYSICS
    • G01—MEASURING; TESTING
    • G01C—MEASURING DISTANCES, LEVELS OR BEARINGS; SURVEYING; NAVIGATION; GYROSCOPIC INSTRUMENTS; PHOTOGRAMMETRY OR VIDEOGRAMMETRY
    • G01C11/00—Photogrammetry or videogrammetry, e.g. stereogrammetry; Photographic surveying

Definitions

  • the present invention relates to imaging systems in which two or more complex signals of a region of interest may be combined to yield one or more interferometric images. More particularly, the invention is directed to a method and system for two-dimensional radiometric imaging of a planetary surface region of interest utilizing thermal radiation emitted by the region of interest.
  • Computed imaging systems are utilized in a wide variety of applications. Of particular interest here is the use of radio frequency antennas to collect complex signals employable to obtain high quality images of planetary surfaces.
  • Such complex images are typically obtained by overhead transmission/reflected receipt of pulses of energy at a predetermined frequency.
  • microwave radiation has been advantageously employed due to its ability to yield high resolution images in virtually all weather conditions and at all times (i.e., day and night).
  • a primary objective of the present invention is to provide an improved imaging system and method that reduces imaging componentry payload and complexity on space vehicles utilized to collect imaging data.
  • Related objectives are to reduce on-board power requirements and componentry costs associated with the obtainment of imaging data on space-borne vehicles.
  • Another important objective of the present invention is to provide a radiometric imaging system and method that is passive in nature and thereby avoids the active transmission of energy signals to an image region of interest to form a pixel image thereof.
  • An additional main objective of the present invention is to provide an imaging system and method that reduces the number of space vehicles and associated antennas necessary for generating high-resolution images.
  • Yet another objective of the present invention is to provide an imaging system and method that provides high-resolution images in inclement weather and day/night conditions.
  • the present inventors have recognized that even though thermal emissions from a planetary surface region of interest are of random phase and amplitude, such emissions may be assumed to be largely isotropic and mutually coherent at a receiving antenna (e.g., as received or time-shifted), and may be collected and processed in a manner that allows such randomness to be effectively removed.
  • thermal radiation collection and processing can be carried out in a manner that reduces the number of antennas necessary to yield high-resolution images.
  • the present invention is particularly apt for radiometric imaging applications, certain aspects may also be employable in active imaging arrangements.
  • the inventive system contemplates a plurality of space vehicles located in known relative positions over a planetary surface region of interest (ROI). At least a corresponding plurality of antennas are mounted on the space vehicles to collect radiation emissions from the ROI (e.g., thermal or blackbody radiation) and provide corresponding thermal emission signals.
  • processor means e.g., one or more signal processors
  • processors may be utilized (e.g., either on-board the space vehicles and/or more preferably at another location) to combine the thermal emission signals and obtain interferometric fringe signals employable to form a pixel image of the ROI.
  • interferometric fringes effectively removes phase randomness from the collected signals.
  • the space vehicles may be spaced at different relative distances therebetween, wherein the collection antennas collectively define a "sparse aperture".
  • the space vehicles may be located so that two or more of the antennas are horizontally and/or vertically offset from each other in relation to the imaged ROI during imaging.
  • each combination yields a different interferometric phase measurement based upon a corresponding different interferometric baseline.
  • the multiple different interferometric phase measurements can effectively "fill-in" an array of interferometric images employable in pixel image formation for the ROI.
  • the differential spacing of antennas to collectively define a sparse aperture facilitates reduction of the overall number of space vehicles required to yield high-resolution ROI images.
  • the space vehicles may be positioned in a "near-field" imaging arrangement to collect thermal emissions from an ROI. That is, the space vehicles may be positioned so that the imaging center axes for at least two of the antennas define an angle ⁇ of at least about 2° therebetween, and more preferably about 2° and 15° therebetween, depending upon the collection center frequency of the antennas.
  • the antennas may be provided to collect thermal emissions over a collection bandwidth of between about 1MHz and 1GHz with a center frequency of between about 1GHz and 100GHz.
  • the establishment of a near-field imaging arrangement also facilitates the obtainment of high-resolution ROI images.
  • a plurality of antennas may be mounted on a corresponding plurality of satellites located in a known constellation passing over an ROI to be imaged. More particularly, two or more satellites may be located in corresponding repeatable orbits having relatively small differences in eccentricity and/or inclination (e.g., Hill's orbits), wherein the corresponding antennas are horizontally and/or vertically offset in a known geometry relative to the ROI for imaging.
  • four satellites may be positioned in known orbits to laterally define a repeatabl _ Y-shaped pattern for sparse aperture imaging.
  • the satellites may be disposed in low-earth orbits, wherein the satellites are placed at altitudes and spacings consistent with near-field operations.
  • the antennas should be provided in a spotlight mode (e.g., via gimbaled mounting) so that they remain pointed at an imaged ROI during an imaging, or "dwell", time period. Further in this regard, the antennas should be provided to collect thermal emissions from overlapping portions of the ROI in a substantially simultaneous manner to maintain mutual coherence. In turn, the thermal emissions collected from the ROI at each of the antennas may be substantially simultaneously sampled at a predetermined frequency (e.g., at least the Nyquist rate) during a given dwell period, thereby yielding an ROI thermal emission data set comprising each thermal emission signal.
  • a predetermined frequency e.g., at least the Nyquist rate
  • the processor means may be provided to combine, or correlate, at least a first thermal emission signal (e.g., collected by the first antenna) with a complex conjugate of at least a second thermal emission signal (e.g., collected by a second antenna) to obtain at least a first "simple" interferometric fringe signal.
  • a first thermal emission signal e.g., collected by the first antenna
  • a second thermal emission signal e.g., collected by a second antenna
  • it is generally preferably to correlate a plurality of different pairs of thermal emission signals to obtain a plurality of different simple interferometric fringe signals.
  • it may be desirable in certain applications to time-shift one of the thermal emission signals of a given pair prior to correlation e.g., in high bandwidth applications.
  • each simple interferometric fringe signal(s) may be low-pass filtered to yield a corresponding averaged, or "smoothed", signals, wherein amplitude randomness is effectively removed.
  • the processor means may correlate at least the first simple interferometric fringe signal and at least one other signal for the ROI (e.g., obtained/generated pursuant to the corresponding-in-time receipt of thermal emissions from the ROI) to obtain at least one "compound" interferometric fringe signal employable in the formation of a pixel image of the ROI.
  • the signal that is combined with the first simple interferometric fringe signal may be one of a first thermal emission signal, second thermal emission signal or third thermal emission signal (e.g., collected by a third antenna), or perhaps more preferably, a second simple interferometric fringe signal obtained by combining one of the first and second thermal emission signals with a complex conjugate of a third thermal emission signal.
  • a first simple interferometric fringe signal (e.g., which correlates thermal emission signals generated by first and second antennas) may be combined with a second simple interferometric fringe signal (e.g., which correlates thermal emission signals generated by third and fourth antennas) to obtain a first compound interferometric fringe signal.
  • simple fringe correlations of the first and third thermal emission signals and of the second and fourth thermal emission signals can be further correlated to obtain a second compound interferometric fringe signal.
  • the first and second compound interferometric fringe signals may be further combined in an additional stage.
  • the formation/utilization of simple interferometric fringes and compound interferometric fringes particularly facilitates a sparse aperture imaging arrangement, thereby reducing the number of space vehicles/antennas needed to generate high-resolution images.
  • the processor means may be provided to extract pixel value (e.g., complex values (i.e., comprising phase and amplitude components) or real amplitude values) from at least one and preferably a plurality of interferometric fringe signals employed for image formation on a per pixel location basis.
  • the extracted pixel values are employable by the processor means to "develop" the pixel image of the ROI.
  • the processor means may provide for the corresponding application of a plurality of different matched filters (e.g., corresponding with each of a plurality of pixel locations for the ROI pixel image to be formed) to obtain a plurality of extracted pixel values in corresponding relation to each of the plurality of pixel locations.
  • the pixel values corresponding with each given pixel location may be utilized to form an interferometric image signal (e.g., for each interferometric fringe signal employed for image formation).
  • the extracted pixel values for each given pixel location may be combined to obtain a corresponding interferometric image signal .
  • the plurality of interferometric image signals corresponding with the plurality of interferometric fringe signals employed may be merged (e.g., via complex summation and/or simple or weighted averaging) to yield the ROI pixel image.
  • the utilization of separate matched filters for each pixel location and each interferometric fringe signal employed facilitates near-field imaging of an ROI as discussed above.
  • an inventive method may comprise the steps of collecting thermal emission from a planetary surface region of interest (ROI) by a plurality of spaced antennas to obtain a corresponding plurality of thermal emission signals. Following collection, the method further includes the step of first combining at least a first thermal emission signal with a complex conjugate of at least a second thermal emission signal to obtain at least a first simple interferometric fringe signal.
  • a plurality of different simple interferometric fringe signals are formed from different pairs of collected thermal emission signals, wherein the data comprising one of each such pairs may be time- shifted to maintain mutual coherence.
  • Each simple interferometric fringe signal may be low-pass filtered to remove undesired high-frequency components and otherwise yield an averaged signal.
  • the inventive method may further comprise the step of second combining at least a first simple interferometric signal with another signal for the ROI (e.g., a signal generated from corresponding-in-time thermal emissions from the ROI) to obtain at least a first compound interferometric fringe signal.
  • the second combining step may provide for the combining of one of the first and second thermal emission signals with the complex conjugate of a third thermal emission signal to obtain a second simple interferometric fringe signal.
  • the noted first compound interferometric fringe signal may be generated by combining a first simple interferometric fringe signal with one of (i) the second simple interferometric fringe signal, and (ii) one of said first, second and third thermal emission image signals.
  • a plurality of different compound interferometric fringe signals are formed.
  • the formation/use of one or more compound interferometric fringe signals in image formation facilitates the use of a sparse aperture arrangement.
  • the inventive method may provide for (i) collecting thermal radiation at the collection antennas over a predetermined frequency bandwidth of about 1MHz to 1GHz, and (ii) positioning at least two of the collection antennas to define an angle of at least about 2° between their respective center imaging axes (e.g., to define a near-field imaging arrangement).
  • the inventive method may include the step of applying a different matched filter corresponding with each of a plurality of pixel locations to interferometric signal data to extract a plurality of pixel values (e.g., complex values or real amplitude values) corresponding with each of said plurality of image pixel locations.
  • a different matched filter corresponding with each of a plurality of pixel locations to interferometric signal data to extract a plurality of pixel values (e.g., complex values or real amplitude values) corresponding with each of said plurality of image pixel locations.
  • the inventive method may include the step of combining the pixel values corresponding with each of the plurality of pixel locations (e.g., summing) and utilizing the combined pixel values to obtain an interferometric image signal employable in the formation of the pixel image of the ROI.
  • the resultant plurality of interferometric images signals may be merged to yield the ROI pixel image.
  • merging may provide for the averaging or weighted averaging of the different interferometric images in generating the ROI pixel image.
  • Fig. 1 illustrates one system embodiment of the present invention.
  • Fig. 2 illustrates satellite ranges for the system embodiment of Fig. 1.
  • Fig. 3 is a schematic illustration of a processor means embodiment employable in the system of Fig. 1.
  • Fig. 4 is a process diagram showing steps employable in the system embodiment of Fig. 1.
  • Fig. 1 illustrates an exemplary system embodiment 10 of the present invention.
  • System 10 includes four space vehicles 20a, 20b, 20c and 20d, each having a collection antenna 22a, 22b, 22c and 22d mounted thereupon for receipt of thermal radiation emitted from a region of interest (ROI) on a planetary surface (e.g., within a circular access region).
  • ROI region of interest
  • antennas 22a, 22b, 22c and 22d should be provided for operation in a spotlight mode, e.g., wherein the antennas are gimbaled relative to the space vehicles to maintain a substantially common footprint over the ROI during imaging operations.
  • the exemplary system 10 further includes a communications space vehicle 30 and ground station 32 for the transmission of control information and/or downloading of thermal emission data collected by antennas 22a, 22b, 22c and 22d.
  • exemplary system 10 may be provided so that thermal emission data collected at space vehicles 20b, 20c and 20d may be relayed to space vehicle 20a for downloading via a communications antenna 24a to ground station 32 and subsequent processing for image formation.
  • the data may be uploaded to and at least partially processed at communications space vehicle 30, then downloaded to ground station 32 for further processing.
  • each of the space vehicles 20a, 20b, 20c and 20d may directly transmit the corresponding collected data for processing at the communications space vehicle 30 and or ground station 32.
  • Space vehicles 20a, 20b, 20c and 20d may be located in known relative positions for imaging.
  • space vehicles 20a, 20b, 20c and 20d may comprise four satellites in a known constellation. That is, the satellites may be disposed in closely-related and repeatable orbits, wherein at least two of the satellites are horizontally offset and at least two of the satellites are vertically offset in a known geometry during imaging. Such horizontal and vertical spacing is preferred so that a predetermined resolution can be achieved with antennas 22a, 22b, 22c and 22d collectively defining a sparse aperture arrangement.
  • Fig. 2 illustrates satellites 20a, 20b, 20c and 20d in an arrangement in which antennas 22a, 22b, 22c, and 22d are disposed at corresponding ranges Rl, R2, R3 and R4 relative to an ROI center point along their respective center imaging axes.
  • range differences between Rl and R2, R2 and R3, and R3 and R4 yield corresponding different baselines ⁇ R ⁇ ,2 , ⁇ R 2 and ⁇ R ;4 for purposes of interferometric measurements.
  • range differences between Rl and R3, Rl and R4, and R2 and R4 yield additional different baselines for interferometric measurements.
  • space vehicles 20a, 20b, 20c and 20d may also be positioned to define a near-field imaging arrangement. That is, and referring again to Fig. 2, space vehicles 20a, 20b, 20c and 20d may be positioned so that the imaging center axes for at least two of the antennas 22a, 22b, 22c and/or 22d define an angle ⁇ ⁇ at least about 2° therebetween, preferably 2° and 15° therebetween, and most preferably between about 6° to 10° therebetween.
  • the antennas 22a, 22b, 22c and 22d may be provided to collect radiation over a bandwidth of about 1MHz to 1GHz with a center frequency of about 1GHz to 100 GHz.
  • space vehicles 20a, 20b, 20c and 20d may be preferably positioned at elevations of no more than about 600nmi, and most preferably between about 200nmi and 500nmi relative to a ROI.
  • four satellites may be located in low-earth orbits of about
  • the satellites may be carried by a single launch vehicle to a predetermined orbital altitude, then deployed from the launch vehicle.
  • thrusters on the satellites may be utilized as needed to define a known constellation with use of an on-board positioning system (e.g., a system referenced to the Global Positioning System (GPS)).
  • GPS Global Positioning System
  • the satellites may be positioned to laterally define a Y-shaped constellation relative to the earth surface. In such an arrangement, the satellites may be located in orbits that yield satellite spacings of between about 60nmi and 120nmi.
  • antennas 22a, 22b, 22c and 22d may be controlled to substantially simultaneously collect thermal radiation emitted from the ROI over a common, predetermined dwell period. Further, and as previously noted, antennas 22a, 22b, 22c and 22d may be provided to collect radiation in a spotlight mode over a collection bandwidth of between about 1MHz and 1GHz, with a center frequency of between about 1GHz and 100GHz. In turn, the collected radiation may be sampled/digitized at antennas 22a, 22b, 22c and 22d (e.g., at a rate of between about 1.2MHz and 1.2GHz) for on-board thermal emission data storage on space vehicles 20a, 20b, 20c and 20d, and subsequent downloading/processing for image formation purposes.
  • Fig. 3 schematically illustrates a processing means embodiment 100 employable in system 10.
  • the digitized thermal emission signals collected by antennas 22a, 22b, 22c and 22d may be introduced for signal processing via corresponding channels 1 10a, 110b, 1 10c and 11 Od.
  • the collected thermal emission signals 1 12a, 1 12b, 112c and 112d may be characterized as a function of time (t) as follows:
  • 1 12d in channels 1 10a, 1 10b, 110c and 1 lOd may be combined in differing permutations, or sets, of two at combiners 120a-120f to obtain interferometric phase differences therebetween. That is, combiners 120a-120f may provide for the mixing of corresponding data samples comprising two different thermal emission signals introduced via channels 120a, 120b, 120c, and 120d to obtain combined, or simple interferometric fringe signals 122a-122f. While not shown, the data comprising one signal of any given pair of signals 1 12a, 1 12b, 1 12c and 1 12d to be combined may be time-shifted in relation to the other signal to ensure mutual coherence.
  • signal mixing at combiners 120a-120f may be achieved via multiplication of one thermal emission signal by the complex conjugate of another thermal emission signal.
  • each combined signal 122a-122f may define a time- varying interference pattern, or simple fringe phase function, over an ROI.
  • processor means embodiment 100 may further provide for the "up-sampling" of the thermal emission signals 1 12a-l 12d (not shown) prior to signal combining at combiners 120a-120f.
  • Such up-sampling may be implemented via software functionality that provides for the interpolation of successive data values comprising signals 1 12a-l 12d to increase the number of data values for further processing.
  • the resultant simple interferometric fringe signals 122a-122f may be low-pass filtered at filters 130a-130f (e.g., at a frequency of about 1MHz or less) so as to remove high frequency components and otherwise yield signal averaging. In the latter regard, such averaging serves to effectively remove amplitude randomness from the collected thermal emissions.
  • the averaged simple interferometric fringe signals 132a-132f may be further combined in differing permutations, or sets, of two at combiners 140a-140o to obtain compound interferometric fringe signals 142a-142o.
  • combiners 140a-140o may provide for the mixing of corresponding data values comprising two different averaged simple interferometric fringe signals 132a- 132f (e.g., via multiplication), wherein each combination will further define a time- varying interference pattern or compound fringe phase function, over an ROI.
  • the down-sampling frequency at filters 130a-130f may be set to preserve Nyquist integrity at combiners 140a-140f.
  • compound fringes at mixers 140a-140o may alternately and/or additionally be obtained by the mixing of any one of the thermal emission image signals 112a, 1 12b, 1 12c or 1 12d with any one of the simple interferometric fringe signals 122a, 122b, 122c, 122d, 122e and/or 122f.
  • the illustrated processing means embodiment 100 provides for the application of matched filters 150a-150o to yield compound signals 152a-152o. More particularly, a separate matched filter corresponding with each of a plurality of pixel locations (e.g., corresponding with the ROI pixel image to be formed) may be applied to each of the data values comprising each of the compound interferometric fringe signals 142a-142o to extract pixel values (e.g., amplitude-containing values) therefrom (e.g., via a simple dot product operation).
  • pixel values e.g., amplitude-containing values
  • matched filters 150a- 150o may be developed on a per pixel location basis in relation to the imaged ROI and the particular combination of averaged simple interferometric fringe signals 132a-132o and/or thermal emission signals 1 12a-l 12d combined at combiners 140a- 140b.
  • Each such matched filter may effectively define the predicted interferometic phase difference, or interferometric phase function, for the given pixel location and the given combination of thermal emission signals 112a- 1 12d and/or averaged simple interferometric fringe signals 122a-122o mixed for interferometric image formation.
  • matched filters may be based on known geometries between each of the antennas 122a, 122b, 122c and 122d, in relation to the ROI, together with terrain data (e.g., elevation data) for the ROI.
  • terrain data e.g., elevation data
  • Such terrain data may be predetermined and/or otherwise derived on a dynamic basis from the complex image signals 112a, 112b, 112c and 112d (e.g., via a split aperture/auto-focus technique).
  • the resultant compound signals 152a-l 52o may be further processed by integration modules 160a-160o to obtain integrated interferometric image signals 162a-162o.
  • modules 160a-160o provide for integration (e.g., summation) of the extracted pixel values corresponding with each given pixel location corresponding with the ROI pixel image to be formed.
  • the integrated pixel values comprising each of the integrated interferometric image signals 162a-162o combinatively define a corresponding interferometric image for use in ROI pixel image formation. That is, each of the integrated interferometric image signals 162a-162o may be merged at merge module 170 to yield a composite interferometic image, or thermal image, of the ROI.
  • the integrated interferometric image signals 162a- 162o may be simply averaged at module 170.
  • module 170 may provide for weighted averaging of the signals 162a-162o, wherein the signals 162a-162o are weighted in a predetermined manner.
  • a third alternative at module 170 may provide for complex summation of data comprising signals 162a-162o.
  • thermal emissions from an ROI may be collected and sampled at a plurality of antennas to obtain a corresponding plurality of thermal emission signals (Step 200).
  • antennas 22a-22d located on corresponding satellites 20a-20d may be employed in a spotlight mode.
  • the satellites 20a-20d may be located so that antennas 22a-22d are disposed in a near field imaging arrangement and so that the antennas 22a-22d collectively define a sparse aperture.
  • at least one and preferably a plurality of simple interferometric fringe signals may be formed (Step 202).
  • thermal emission signals 1 12a-l 12d may be multiplied at combiners 120a-120f to form simple interferometric fringe signals 122a-122f.
  • the simple interferometric fringe signal(s) may be utilized to form a pixel image of the region of interest (Step 204).
  • the simple interferometric fringe signal(s) may be filtered (Step 206) in order to remove high-frequency components and correspondingly average each of the signal.
  • low-pass filters 130a-130f may be utilized for such signal averaging.
  • At least two averaged simple interferometric fringe signals may be combined to obtain at least one compound interferometric fringe signal (Step 208).
  • the formation of compound interferometric fringe signal(s) 142a-142o may entail the multiplication of averaged simple interferometric fringe signals 132a-132f at combiners 140a-140o.
  • multiple successive levels of compound fringe signals may be formed from compound fringe signals formed in a preceding stage.
  • pixel values may be extracted therefrom for each of a plurality of pixel locations (Step 210). Such pixel locations correspond with the ROI pixel image to be formed.
  • the extracted pixel values may be utilized to generate a pixel image (Step 212).
  • the extracted pixel values for each given interferometric fringe signal may be combined to generate a corresponding interferometric image or image signal.
  • such interferometric image(s) may be employed to generate an ROI pixel image.
  • the extraction of pixel values from the interferometric fringe signals may entail the development of matched filters for each of a plurality of pixel locations in corresponding relation to each given interferometric fringe signal employed for image formation (Step 214). In turn, such matched filters may be applied in corresponding relation to each interferometric fringe signal on a pixel location-specific basis (Step 216).
  • matched filters 150a-150o may be employed for pixel value extraction.
  • the extracted pixel values for each given pixel location may be integrated at integration modules 160a-160d to yield corresponding interferometric image signals 162a-162o.
  • signals 162a-162o may be merged at module 170 for pixel image formation.

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  • Physics & Mathematics (AREA)
  • General Physics & Mathematics (AREA)
  • Radar, Positioning & Navigation (AREA)
  • Remote Sensing (AREA)
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Abstract

La présente invention concerne un procédé et un système permettant la représentation d'une zone d'intérêt (region of interest / ROI) de la surface planétaire. Dans le cadre d'une première application, une pluralité de véhicules spatiaux surmontés d'antennes servent à recueillir des rayonnements thermiques émis à partir de la ROI, et à produire des signaux d'émission thermiques correspondants. Des signaux d'émission thermiques de ce type peuvent être combinés pour obtenir une ou plusieurs franges interférométriques simples. Les franges simples peuvent être utilisées pour obtenir une image pixelisée de la ROI. Dans un aspect de l'invention, une ou plusieurs franges interférométriques simples peuvent être utilisées pour produire une ou plusieurs franges interférométriques composées destinées à être utilisées pour la formation de l'image pixelisée. Une ou plusieurs franges composées peuvent être utilisées pour produire des niveaux supplémentaires de franges composées destinés à être utilisés pour la formation de l'image pixelisée. Dans un autre aspect de l'invention, les véhicules spatiaux peuvent se trouver dans une disposition de représentation 'à champ proche' par rapport à la ROI et une approche de filtrage compatible peut être utilisée pour extraire les données d'amplitude de(s) frange(s) interférométrique(s) sur une base destinée à être utilisée pour la formation d'images pixelisées.
PCT/US2000/033294 1999-12-07 2000-12-07 Procede et systeme de radiometrie interferometrique bi-dimensionnelle Ceased WO2001048439A2 (fr)

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US20020074498A1 (en) 2002-06-20
US6452181B1 (en) 2002-09-17
AU5514901A (en) 2001-07-09
US20020074497A1 (en) 2002-06-20
US6586741B2 (en) 2003-07-01
WO2001048439A3 (fr) 2002-01-24
US20020134941A1 (en) 2002-09-26
US6441376B1 (en) 2002-08-27

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